CN102323962A - Blade of aviation engine profile runner line measuring route planing method - Google Patents
Blade of aviation engine profile runner line measuring route planing method Download PDFInfo
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- CN102323962A CN102323962A CN201110132963A CN201110132963A CN102323962A CN 102323962 A CN102323962 A CN 102323962A CN 201110132963 A CN201110132963 A CN 201110132963A CN 201110132963 A CN201110132963 A CN 201110132963A CN 102323962 A CN102323962 A CN 102323962A
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Abstract
The present invention proposes a kind of blade of aviation engine profile runner line measuring route planing method; At first blade profile and blade listrium are carried out parametric modeling; Then with blade profile and blade listrium curved surface along its normal orientation outwards setover out blade profile biasing surface and blade listrium curved surface biasing surface; Adopt blade listrium curved surface biasing surface that the blade profile biasing surface is carried out cutting; And the blade profile biasing surface carried out parametric modeling again, structure waits parameter line group T along the v direction on the blade profile biasing surface
i, with each bar parameter line T
i, discrete is four curves: blade back runner line, leaf basin runner line, leading edge runner line and trailing edge runner line; On leading edge runner line and trailing edge runner line, the measurement point number in the 1mm is not less than 10, and on blade back runner line and leaf basin runner line, measurement point spacing δ should be in δ≤15mm scope.Measuring route line of the present invention is the curve of a sealing, is easy in reverse-engineering, carry out solid modelling.
Description
Technical field
The present invention relates to the engine blade measuring technique, be specially a kind of blade of aviation engine profile runner line measuring route planing method.
Background technology
The planning of measuring route is a key issue during free form surface is measured, and its purpose is exactly to make measuring head reach the measurement purpose with path safety of lacking as far as possible and the surveyed area that travels through curved surface to be measured efficiently.The quality of measuring route directly affects the precision of efficiency of measurement and reconstruct curved surface.
The following factor of considered when the patch measuring route is planned: (1) measuring route should be able to reflect the actual conditions of tested curved surface; (2) measuring route should meet the curved surface structure mode of CAD/CAM system; (3) curved surface of measurement data reconstruct in CAD/CAM system should be easy to extend, with remedy measurement less than the dough sheet zone, and extended surface should be able to reflect the patch actual conditions.
Aspect the planning of blade profile measuring route, should in CAD software, realize the automatic generation of measurement point for the automatic measurement that realizes blade according to the cad model of blade.The selection of measurement point is the key factor that influences measuring accuracy and efficiency of measurement.It is to wait the high measurement path that blade is measured the most frequently used three coordinate measuring engine measurement path; The subject matter of this method is because the difference of blade inlet edge length and trailing edge length causes the measuring route thread breakage through regular meeting, is unsuitable for and in reverse-engineering, carries out solid modelling; Be difficult to carry out follow-up CAD/CAM curved surface structure; And high path measurements method such as employing also distributes on the data processing of measurement point and handles, and follow-up CAD/CAM curved surface structure is caused problems such as calculated amount is big.
Summary of the invention
The technical matters that solves
Wait the high measurement path as the problem that blade of aviation engine profile measurement path exists for solving existing employing, the present invention proposes a kind of blade of aviation engine profile runner line measuring route planing method.
Technical scheme
Technical scheme of the present invention is:
A kind of blade of aviation engine profile runner line measuring route planing method is characterized in that: may further comprise the steps:
Step 1: blade profile and blade listrium are carried out parametric modeling according to the theoretical cross-section data of blade;
Step 2: along the outside equidistance of its normal orientation blade profile biasing surface of setovering out, the distance between blade profile and the blade profile biasing surface is the gauge head radius R of measuring machine with the blade profile after the parametrization that obtains in the step 1;
Step 3: along the outside equidistance of its normal orientation blade listrium curved surface biasing surface of setovering out, the distance between blade listrium curved surface and the blade listrium curved surface biasing surface is r+R with blade listrium curved surface, and wherein r is the knuckle radius of blade listrium curved surface and blade profile;
Step 4: adopt blade listrium curved surface biasing surface that the blade profile biasing surface is carried out cutting, the blade profile biasing surface after the cutting is carried out parametric modeling again;
Step 5: the blade profile biasing surface of the Reparameterization that step 4 obtains is expressed as S
0, be defined as the u parametric direction along the section line direction of blade profile biasing surface, be defined as the v parametric direction along the radial direction of blade profile biasing surface, parameters u, v is at S
0Interior span standard turns to [0,1]; At S
0Last structure is along the T such as group such as parameter line such as grade of v direction
i: { T
i, i=1,2 ..., n};
Step 6: with each bar parameter line T
i, according to the position of blade profile biasing surface of living in, discrete is four curves: blade back runner line, leaf basin runner line, leading edge runner line and trailing edge runner line;
Step 7: on leading edge runner line and trailing edge runner line, the measurement point number in the 1mm is not less than 10, and on blade back runner line and leaf basin runner line, measurement point spacing δ should be in δ≤15mm scope.
Beneficial effect
The blade of aviation engine profile runner line measuring route planing method that adopts the present invention to propose; Can avoid the fracture of measuring route curve, the approximate path of airflow passes blade profile when the measuring route line that forms in this method is blade working is the curve of a sealing; So be easy in reverse-engineering, carry out solid modelling; And the measurement point position is easy to control on this closed flow line, on follow-up measurement point data processing, also is bulk treatment, makes follow-up calculated amount reduce greatly.
Description of drawings
Fig. 1: the measuring route curve and the measurement point synoptic diagram that adopt the present invention to obtain.
Embodiment
Below in conjunction with specific embodiment the present invention is described.
Embodiment:
Present embodiment carries out measuring route planning for the blade profile runner line measuring route planing method that adopts the present invention's proposition to certain type blade of aviation engine profile.
Step 1: adopt the CAD modeling software, blade profile and blade listrium are carried out parametric modeling according to the theoretical cross-section data of vane motor blade;
Step 2: with the blade profile after the parametrization that obtains in the step 1 along outwards setover out the blade profile biasing surface of an equidistance of its normal orientation; Distance between blade profile and the blade profile biasing surface is the gauge head radius R of measuring machine; What adopt in the present embodiment is three coordinate measuring machine, and the gauge head radius R is 1mm;
Step 3: with blade listrium curved surface along the outside equidistance of its normal orientation blade listrium curved surface biasing surface of setovering out; Distance between blade listrium curved surface and the blade listrium curved surface biasing surface is r+R; Wherein r is the knuckle radius of blade listrium curved surface and blade profile, and the blade listrium curved surface of present embodiment engine blade and the knuckle radius r of blade profile are 2mm;
Step 4: in the CAD modeling software, adopt blade listrium curved surface biasing surface that the blade profile biasing surface is carried out cutting, and the blade profile biasing surface after the cutting is carried out parametric modeling again;
Step 5: the blade profile biasing surface of the Reparameterization that step 4 is obtained is expressed as S
0, the section line direction of blade profile biasing surface is defined as the u parametric direction, and the radial direction of blade profile biasing surface is defined as the v parametric direction, parameters u, v is at S
0Interior span standard turns to [0,1]; In the CAD modeling software, at S
0The last Ti:{Ti such as group such as parameter line such as grade that constructs along the v direction, i=1,2 ..., n}, n gets 9 in the present embodiment;
Step 6: with each the bar parameter line T in 9 parameter lines
i, all according to the position of its blade profile biasing surface of living in: blade back, leaf basin, blade inlet edge and trailing edge, discrete is four curves: blade back runner line, leaf basin runner line, leading edge runner line and trailing edge runner line;
Step 7: the blade edge head partly separates measurement with blade, leading edge runner line line length 1.8mm wherein, and discrete measurement point is 20; Trailing edge runner line line length is 2.1mm; Discrete measurement point is 20, and blade back runner line line length is 150mm, and discrete measurement point is 10; Leaf basin runner line line length is 142mm, and discrete measurement point is 10.
Thus, the blade profile runner line measuring route planing method that adopts the present invention to propose has been accomplished the measuring route planning to this blade of aviation engine profile.
Fig. 1 obtains measuring route curve and measurement point for present embodiment, according to these measurement points measure and coupling after, with the blade profile error of theoretical model be 0.075, position error 0.092, torsional error are-7.72 '.These three errors prove that this method is feasible all in the scope of drawing requirement the time.
Claims (1)
1. blade of aviation engine profile runner line measuring route planing method is characterized in that: may further comprise the steps:
Step 1: blade profile and blade listrium are carried out parametric modeling according to the theoretical cross-section data of blade;
Step 2: along the outside equidistance of its normal orientation blade profile biasing surface of setovering out, the distance between blade profile and the blade profile biasing surface is the gauge head radius R of measuring machine with the blade profile after the parametrization that obtains in the step 1;
Step 3: along the outside equidistance of its normal orientation blade listrium curved surface biasing surface of setovering out, the distance between blade listrium curved surface and the blade listrium curved surface biasing surface is r+R with blade listrium curved surface, and wherein r is the knuckle radius of blade listrium curved surface and blade profile;
Step 4: adopt blade listrium curved surface biasing surface that the blade profile biasing surface is carried out cutting, the blade profile biasing surface after the cutting is carried out parametric modeling again;
Step 5: the blade profile biasing surface of the Reparameterization that step 4 obtains is expressed as S
0, the section line direction of blade profile biasing surface is defined as the u parametric direction, and the radial direction of blade profile biasing surface is defined as the v parametric direction, parameters u, v is at S
0Interior span standard turns to [0,1]; At S
0Last structure is along the T such as group such as parameter line such as grade of v direction
i: { T
i, i=1,2 ..., n};
Step 6: with each bar parameter line T
i, according to the position of blade profile biasing surface of living in, discrete is four curves: blade back runner line, leaf basin runner line, leading edge runner line and trailing edge runner line;
Step 7: on leading edge runner line and trailing edge runner line, the measurement point number in the 1mm is not less than 10, and on blade back runner line and leaf basin runner line, measurement point spacing δ should be in δ≤15mm scope.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110132963 CN102323962B (en) | 2011-05-20 | 2011-05-20 | Blade profile runner line measuring path planning method for aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110132963 CN102323962B (en) | 2011-05-20 | 2011-05-20 | Blade profile runner line measuring path planning method for aircraft engine |
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| CN102323962A true CN102323962A (en) | 2012-01-18 |
| CN102323962B CN102323962B (en) | 2012-12-26 |
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| CN 201110132963 Expired - Fee Related CN102323962B (en) | 2011-05-20 | 2011-05-20 | Blade profile runner line measuring path planning method for aircraft engine |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103116679A (en) * | 2013-03-01 | 2013-05-22 | 西北工业大学 | Aviation blade oval leading and trailing edge process model generation method |
| CN103411574A (en) * | 2013-08-14 | 2013-11-27 | 西北工业大学 | Aviation engine blade profile three-coordinate measuring method |
| CN103433804A (en) * | 2013-08-27 | 2013-12-11 | 西北工业大学 | Impeller machining cutter-axis vector control method based on five-axis interference-free cutter axis control line |
| CN103486996A (en) * | 2013-08-14 | 2014-01-01 | 西北工业大学 | Measuring method for unknown aviation engine blade profile of CAD model |
| CN103557774A (en) * | 2013-11-19 | 2014-02-05 | 哈尔滨电气动力装备有限公司 | Nuclear main pump impeller wing section detection method |
| CN104330068A (en) * | 2014-11-05 | 2015-02-04 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for reducing three-coordinate measuring compensating error of blade surface |
| CN104864829A (en) * | 2015-06-14 | 2015-08-26 | 吉林大学 | Quick measurement method for blade curved surface |
| CN105627923A (en) * | 2016-01-08 | 2016-06-01 | 黑龙江科技大学 | Scan path programming method obtained by leaf dense point cloud on basis of laser ranging |
| CN107228610A (en) * | 2017-05-03 | 2017-10-03 | 华中科技大学 | A kind of spiral scan for tubular curved surface measures method for planning track |
| CN112414354A (en) * | 2020-12-15 | 2021-02-26 | 西安飞机工业（集团）有限责任公司 | Method for planning appearance measuring points of curved surface part |
| CN113158269A (en) * | 2021-01-29 | 2021-07-23 | 哈尔滨工业大学 | Space STL curved surface equidistant path planning method in curved surface layered additive manufacturing |
| CN116502369A (en) * | 2023-06-25 | 2023-07-28 | 中国航发四川燃气涡轮研究院 | Turbine blade edge plate heat exchange boundary construction method |
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Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103116679A (en) * | 2013-03-01 | 2013-05-22 | 西北工业大学 | Aviation blade oval leading and trailing edge process model generation method |
| CN103116679B (en) * | 2013-03-01 | 2015-07-01 | 西北工业大学 | Aviation blade oval leading and trailing edge process model generation method |
| CN103411574B (en) * | 2013-08-14 | 2016-01-20 | 西北工业大学 | Blade of aviation engine profile three-coordinate measuring method |
| CN103411574A (en) * | 2013-08-14 | 2013-11-27 | 西北工业大学 | Aviation engine blade profile three-coordinate measuring method |
| CN103486996A (en) * | 2013-08-14 | 2014-01-01 | 西北工业大学 | Measuring method for unknown aviation engine blade profile of CAD model |
| CN103486996B (en) * | 2013-08-14 | 2016-01-20 | 西北工业大学 | The blade of aviation engine profile measurement method of unknown cad model |
| CN103433804A (en) * | 2013-08-27 | 2013-12-11 | 西北工业大学 | Impeller machining cutter-axis vector control method based on five-axis interference-free cutter axis control line |
| CN103433804B (en) * | 2013-08-27 | 2015-10-07 | 西北工业大学 | Based on five axles without the Impeller Machining generating tool axis vector control method of interfering knife-axial controlling line |
| CN103557774A (en) * | 2013-11-19 | 2014-02-05 | 哈尔滨电气动力装备有限公司 | Nuclear main pump impeller wing section detection method |
| CN103557774B (en) * | 2013-11-19 | 2016-08-17 | 哈尔滨电气动力装备有限公司 | Core main pump impeller aerofoil profile detection method |
| CN104330068A (en) * | 2014-11-05 | 2015-02-04 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for reducing three-coordinate measuring compensating error of blade surface |
| CN104330068B (en) * | 2014-11-05 | 2017-03-29 | 沈阳黎明航空发动机(集团)有限责任公司 | It is a kind of to reduce the method that blade profile three-dimensional coordinates measurement compensates error |
| CN104864829A (en) * | 2015-06-14 | 2015-08-26 | 吉林大学 | Quick measurement method for blade curved surface |
| CN104864829B (en) * | 2015-06-14 | 2017-06-27 | 吉林大学 | A kind of method for fast measuring of spoon of blade |
| CN105627923A (en) * | 2016-01-08 | 2016-06-01 | 黑龙江科技大学 | Scan path programming method obtained by leaf dense point cloud on basis of laser ranging |
| CN105627923B (en) * | 2016-01-08 | 2017-10-20 | 黑龙江科技大学 | A kind of planning parameters of scanning paths method that blade dense point cloud based on laser ranging is obtained |
| CN107228610A (en) * | 2017-05-03 | 2017-10-03 | 华中科技大学 | A kind of spiral scan for tubular curved surface measures method for planning track |
| CN107228610B (en) * | 2017-05-03 | 2019-04-12 | 华中科技大学 | A kind of spiral scan measurement method for planning track for tubular curved surface |
| CN112414354A (en) * | 2020-12-15 | 2021-02-26 | 西安飞机工业（集团）有限责任公司 | Method for planning appearance measuring points of curved surface part |
| CN113158269A (en) * | 2021-01-29 | 2021-07-23 | 哈尔滨工业大学 | Space STL curved surface equidistant path planning method in curved surface layered additive manufacturing |
| CN113158269B (en) * | 2021-01-29 | 2022-08-02 | 哈尔滨工业大学 | Space STL curved surface equidistant path planning method in curved surface layered additive manufacturing |
| CN116502369A (en) * | 2023-06-25 | 2023-07-28 | 中国航发四川燃气涡轮研究院 | Turbine blade edge plate heat exchange boundary construction method |
| CN116502369B (en) * | 2023-06-25 | 2023-09-19 | 中国航发四川燃气涡轮研究院 | Turbine blade edge plate heat exchange boundary construction method |
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